[Federal Register Volume 60, Number 121 (Friday, June 23, 1995)]
[Rules and Regulations]
[Pages 32583-32585]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-15013]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-CE-27-AD; Amendment 39-9283; AD 95-13-02]
Airworthiness Directives; Twin Commander Aircraft Corporation
685, 690, and 695 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
[[Page 32584]] applies to certain Twin Commander Aircraft Corporation
(Twin Commander) 685, 690, and 695 series airplanes. This action
requires initially inspecting the vertical stabilizer for cracks,
modifying any cracked vertical stabilizer, and, if not cracked, either
repetitively inspecting or modifying the vertical stabilizer. Several
reports of the vertical stabilizer cracking in different areas prompted
this action. The actions specified by this AD are intended to prevent
failure of the vertical stabilizer as a result of cracking, which, if
not detected and corrected, could result in loss of control of the
airplane.
DATES: Effective July 22, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 22, 1995.
ADDRESSES: Service information that applies to this AD may be obtained
from the Twin Commander Aircraft Corporation, 19010 59th Drive, N.E.,
Arlington, Washington 98223. This information may also be examined at
the Federal Aviation Administration (FAA), Central Region, Office of
the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. David D. Swartz, Aerospace
Engineer, FAA, Northwest Mountain Region, 1601 Lind Avenue S.W.,
Renton, Washington 98055-4056; telephone (206) 227-2624; facsimile
(206) 227-1181.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to certain Twin Commander Models 685, 690, 690A, 690B, 690C, 690D, 695,
and 695A airplanes was published in the Federal Register on February 1,
1995 (60 FR 6045). The action proposed to require initially inspecting
the vertical stabilizer for cracks, modifying any cracked vertical
stabilizer, and, if not cracked, either repetitively inspecting or
modifying the vertical stabilizer. Accomplishment of the proposed
actions would be in accordance with Twin Commander Service Bulletin No.
218, dated May 19, 1994, including Revision Notices 1 and 2, dated July
11, 1994, and September 23, 1994, respectively.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
The FAA estimates that 469 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 10 workhours per
airplane to accomplish the required inspection, and that the average
labor rate is approximately $60 an hour. Parts to accomplish the
required inspection cost approximately $200 per airplane. Based on
these figures, the total cost impact of this AD on U.S. operators is
estimated to be $375,200. This figure does not take into account the
cost of repetitive inspections or the cost of any modifications that
may be needed based on the inspection results. The FAA has no way of
determining how many vertical stabilizers may be cracked and need
modification, or how many repetitive inspections each owner/operator
may incur.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting the Rules Docket at the location provided under the
caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new AD to read as follows:
95-13-02 Twin Commander Aircraft Corporation: Amendment 39-9283;
Docket No. 94-CE-27-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category, that do not have the vertical
stabilizer modified in accordance with the ACCOMPLISHMENT
INSTRUCTIONS: PART II--MODIFICATION section of Twin Commander
Service Bulletin (SB) No. 218, dated May 19, 1994, including
Revision Notices 1 and 2, dated July 11, 1994, and September 23,
1994, respectively:
------------------------------------------------------------------------
Model Serial numbers
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685................................ 12000 through 12066.
690................................ 11000 through 11079.
690A............................... 11100 through 11344.
690B............................... 11350 through 11566.
690C............................... 11600 through 11735.
690D............................... 15001 through 15042.
695................................ 95000 through 95084.
695A............................... 96001 through 96100.
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Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (f) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required upon the accumulation of 2,000 hours time-
in-service (TIS) on a vertical stabilizer or within the next 50
hours TIS after the effective date of this AD, whichever occurs
later, unless already accomplished, and thereafter as indicated in
the body of this AD. [[Page 32585]]
To prevent failure of the vertical stabilizer as a result of
cracks, which, if not detected and corrected, could result in loss
of control of the airplane, accomplish the following:
(a) Inspect the vertical stabilizer for cracks in accordance
with the ACCOMPLISHMENT INSTRUCTIONS: PART I--INSPECTION section of
Twin Commander SB No. 218, dated May 19, 1994, including Revision
Notices 1 and 2, dated July 11, 1994, and September 23, 1994,
respectively.
(b) If damage or cracks are found within the limits of Figures 1
and 2 of the service information referenced above, prior to further
flight, modify the vertical stabilizer in accordance with the
ACCOMPLISHMENT INSTRUCTIONS: PART II--MODIFICATION section of Twin
Commander SB No. 218, dated May 19, 1994, including Revision Notices
1 and 2, dated July 11, 1994, and September 23, 1994, respectively.
(c) If damage or cracks are found outside the limits referenced
in Figures 1 and 2 of the service information referenced above or if
cracks intersect, prior to further flight, replace the damaged parts
with new parts in accordance with the applicable maintenance manual
instructions. The requirements of this AD still apply when the
damaged parts are replaced, unless the stabilizer is modified as
specified in paragraph (b) of this AD.
(d) If no cracks are found, accomplish one of the following:
(1) Reinspect at intervals not to exceed 500 hours TIS, and
modify any damaged or cracked vertical stabilizer as specified in
paragraphs (b) and (c) of this AD; or
(2) Prior to further flight, modify the vertical stabilizer in
accordance with the ACCOMPLISHMENT INSTRUCTIONS: PART II--
MODIFICATION section of Twin Commander SB No. 218, dated May 19,
1994, including Revision Notices 1 and 2, dated July 11, 1994, and
September 23, 1994, respectively.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(f) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, Northwest Mountain Region, 1601
Lind Avenue S.W., Renton, Washington 98055-4056. The request shall
be forwarded through an appropriate FAA Maintenance Inspector, who
may add comments and then send it to the Manager, Seattle ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(g) The inspections and modification required by this AD shall
be done in accordance with Twin Commander Service Bulletin 218,
dated May 19, 1994, including Revision Notices 1 and 2, dated July
11, 1994, and September 23, 1994, respectively. This incorporation
by reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Twin Commander Aircraft Corporation, 19003 59th Drive,
NE., Arlington, Washington 98223. Copies may be inspected at the
FAA, Central Region, Office of the Assistant Chief Counsel, Room
1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(h) This amendment (39-9283) becomes effective on July 22, 1995.
Issued in Kansas City, Missouri, on June 13, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-15013 Filed 6-22-95; 8:45 am]
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